Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Abstract: A combined stand-by instrument intended to be fitted to the instrument panel of an aircraft, and a method for calibrating the combined stand-by instrument, comprises anemobarometric sensors, inertial sensors, a magnetic field sensor, a screen and a computer making it possible to determine and to display on the screen an altitude, a speed, an attitude and a current heading of the aircraft on the basis of the sensors and to calibrate the magnetic field sensor. The computer is configured to allow the simultaneous display on the screen of the altitude, of the speed and of the attitude of the aircraft as well as a guide for the calibration of the magnetic field sensor.

Abstract: The invention relates to a system for estimating flight parameters of an aircraft, having a plurality of static pressure ports and a plurality of measuring probes, each measuring probe having an aerial portion and an electronic device configured to estimate the flight parameters. A first and second measuring probe have identical aerial portions and identical electronic devices, a third measuring probe has an aerial portion and an electronic device that are different from those of the first measuring probe; the electronic devices of the first, second and third measuring probes and the static pressure ports are connected so as to form a first, second and a third data system respectively associated with a static pressure port, and each static pressure port of each of the data systems is separate from each static pressure port of the other data systems.

Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.

Abstract: A combined stand-by instrument intended to be fitted to the instrument panel of an aircraft, and a method for calibrating the combined stand-by instrument, comprises anemobarometric sensors, inertial sensors, a magnetic field sensor, a screen and a computer making it possible to determine and to display on the screen an altitude, a speed, an attitude and a current heading of the aircraft on the basis of the sensors and to calibrate the magnetic field sensor. The computer is configured to allow the simultaneous display on the screen of the altitude, of the speed and of the attitude of the aircraft as well as a guide for the calibration of the magnetic field sensor.

Abstract: A device is provided for backing up calibration information for an air navigation instrument intended to be installed in an aircraft, the air navigation instrument comprising a first connector intended to be connected to a second connector belonging to the aircraft. The invention also relates to an aircraft instrument panel including the device. According to the invention, the backup device is connected between the first and the second connectors. The device comprises a third connector similar to the first connector and connected to the second connector and a fourth connector similar to the second connector and connected to the first connector. All the links from the second connector pass through the device to the fourth connector with no electrical interaction with the device. The device comprises backup means, connected only to the air navigation instrument, by means of the first and fourth connectors.

Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.

Abstract: A device for fastening an optical unit to an actuating ring of an actuating device including a fastening ring joined to the actuating ring and having a plurality of securing shims bonded to the optical unit and connected to the fastening ring by flexible axial tongues. The device can be applied to a triaxial laser gyrometer.

Abstract: In the disclosed laser gyrometer, the three resonant optical cavities of the block are connected to a cathode chamber by means of the three cathode capillary tubes and to a balancing chamber by means of three balancing capillary tubes. The axis of the cathode is identified with the axis of actuation. The block is actuated by means of an actuating ring in thermal contact with the cathode so as to provide for dissipation of the heat generated at the cathode. The invention makes it possible to solve the problems relating to wobble (or lack of dynamic balance) as well as thermal gradients.